Methods and apparatuses for assembling a gas turbine engine

Abstract

A method for assembling a gas turbine engine includes coupling a first structure within the gas turbine engine, wherein the first structure includes a plurality of sockets extending from a radially outer surface of the first structure, and coupling a second structure to the first structure by inserting a radial pin through the second structure and into each respective socket such that the first structure is aligned axially, circumferentially, and with respect to an engine centerline axis extending through the gas turbine engine, where the position of the pins relative to the second structure is adjustable.

Description

BACKGROUND OF THE INVENTION [0001] This invention relates generally to gas turbine engines, and more particularly to methods and apparatus for assembling gas turbine engines. [0002] At least some known gas turbine engines include axisymmetric structures, such as combustors for example. During operation, thermal differentials between the concentric axisymmetric flowpath components may result in thermal stresses being induced. Although providing for relative radial movement between the concentric axisymmetric structures may facilitate reducing such thermal stresses, such arrangements make it more difficult to maintain at least some of the axisymmetric hardware substantially concentric to the engine centerline axis to facilitate proper operation of the gas turbine engine. Moreover, thermal differentials between the axisymmetric structures may result in excessive loads resulting in relatively high cyclic stress and / or fatigue cracks in the axisymmetric structures. [0003] For example, as...

AI Technical Summary

Problems solved by technology

During operation, thermal differentials between the concentric axisymmetric flowpath components may result in thermal stresses being induced.

Although providing for relative radial movement between the concentric axisymmetric structures may facilitate reducing such thermal stresses, such arrangements make it more difficult to maintain at least some of the axisymmetric hardware substantially concentric to the engine centerline axis to facilitate proper operation of the gas turbine engine.

Moreover, thermal differentials between the axisymmetric structures may result in excessive loads resulting in relatively high cyclic stress and / or fatigue cracks in the axisymmetric structures.

As such, these radial pins may experience increased wear compared to other radial pins utilized to support the combustor.

In addition, slight dimensional misalignment of either the pins, the bushing bores, or both, may cause the load to be concentrated on either the edge of the bushing and / or the end of the pin.

This concentrated load on what is initially a point contact on the pin and / or bushing again may result in increased wear of the bushing and / or the pin.

Images